ALERT 

TRANSLATION OF

BOLLETTINO TECNICO N° 109EP-30 

The technical content of this document is approved

under the authority of DOA nr. EASA.21J.005 .

 DATE June 21, 2002

 REV. C September 29, 2006

Compliance with

this bulletin is: 

 ALERT Page 1 of 18

SUBJECT: INSPECTION FOR CRACKS OF TAIL ROTOR BLADES 

P/N 109-8132-01-111, THEIR REPLACEMENT AND TAIL ROTOR GRIP 

BUSHINGS REPLACEMENT. 

REASON: Prescribe checks/inspections to verify for the possible presence of cracks on 

the tail rotor blades P/N 109-8132-01-111 (on both upper and lower surfaces). 

In addition, replacement of the bushings P/N 109-0132-55 with new bushing 

P/N 109-8131-29-101 in order to reduce blade loads and the installation of a 

new pair of tail rotor blades P/N 109-8132-01-111. 

Furthermore cancellation of the Vne limitations. 

HELICOPTERS AFFECTED:

PART I^:

All Agusta A109E helicopters that install hub and blades assy 

P/N 109-8131-02-151. 

PART II^ and PART III^:

All Agusta A109E helicopters that install tail rotor blades P/N 

109-8132-01-111. 

PART IV^ and PART V^:

All Agusta A109E helicopters that install hub and blades assy 

P/N 109-8131-02-151. 

PART VI^:

All Agusta A109E helicopters affected by PART V^ of this Bollettino. 

C 

C 
B.T. 109EP-30 

Page 2 of 18 

COMPLIANCE:

PART I^:

Upon receipt of this Bollettino until compliance with PART IV^ of this Bollettino. 

PART II^:

• For helicopters that adopt the “Standard Inspection Program ”: 

Each airworthiness check and at each pilot’s preflight check. 

• For helicopters that adopt the “Extended Inspection Program” and the 

“Progressive Inspection Program ”: 

Each pilot’s daily preflight check and at each pilot’s preflight check. 

PART III^:

Each 25 (twenty-five) operating hours from receipt of this Bollettino or however 

if any abnormal increase of vibratory level should arise. 

PART IV^:

Upon accomplishment of 200 (two hundred) operating hours of each tail rotor 

blade P/N 109-8132-01-111. 

WARNING

For helicopters equipped with tail 

rotor blades P/N 109-8132-01-111, 

which upon receipt of this Bollettino 

have reached 200 (two hundred) or 

more operating hours. Comply with 

this PART of the Bollettino within 10 

(ten) operating hours from receipt of 

this Bollettino. 

During this time interval, the check 

prescribed in PART III^ shall be

accomplished. At each daily preflight 

check and however each 5 (five) 

operating hours or if any abnormal 

increase of vibratory level should 

arise. 

CAUTION

Any spare tail rotor blades that have 

accumulated service hours on the 

A109E and/or A119 helicopter 

models, may be used only up to 200 

(two hundred) operating hours 

maximum. Upon reaching this limit, 

the blades shall be removed from 

service.
B.T. 109EP-30 

Page 3 of 18 

PART V^:

Within and not later than May 31, 2003. 

CAUTION

The new blades installed on hub and 

grips P/N 109-8131-02-159 (that 

install bushing P/N 

109-8131-30-109) maintain the same 

retirement life of 1000 hours as 

reported in Chapter 04 of the A109E 

Maintenance Manual. 

PART VI^:

C Each 200 (two hundred) flight hours from compliance with PART V^. 

DESCRIPTION:

On an in-service A109E helicopter, a case of a crack on a tail rotor blade 

P/N 109-8132-01-111 has occurred, without any consequence to the 

continuation of the flight mission. 

The crack was detected during a post flight inspection following an abnormal 

increase in ground vibratory level. 

Whilst awaiting compliance with PART V^ of this Bollettino, a Vne limitation is 

introduced in order to decrease the loads on the tail rotor blades. 

Agusta subsequently designed a new bushing P/N 109-8131-30-109, that 

when installed on tail rotor grip assy P/N 109-8131-29-101, reduces the loads

acting upon the tail rotor blades. 

In addition, as a precautionary measure and whilst awaiting modification of the 

configuration as prescribed in PART V^, the tail rotor blade P/N 

109-8132-01-111 retirement life is reduced to 200 (two hundred) operating 

hours. 

This Bollettino therefore prescribes: 

• a reduction of all Vne by 28 KIAS including optional equipment

(PART I^); 

• a visual check by the pilot and/or qualified personnel (PART II^); 

• a visual inspection with the aid of a magnifying glass by qualified 

personnel and, if necessary, a liquid penetrant inspection (PART III^); 

• for tail rotor blades P/N 109-8132-01-111 installed on the grip assy 

P/N 109-8131-02-127, reduction of retirement life to 200 (two hundred)

operating hours (PART IV^); 
B.T. 109EP-30 

Page 4 of 18 

• the replacement of the bushings P/N 109-0132-55 and spacer 

P/N 109-0132-13 with bushing P/N 109-8131-30-109 on tail rotor grip 

P/N 109-8131-29-101 together with the installation of a new pair of tail 

rotor blades P/N 109-8132-01-111 (PART V^). 

This replacement permits: 

3⁄4 cancellation of the Vne limitations prescribed in PART I^, thus 

returning to the values reported in the pertinent A109E Rotorcraft 

Flight Manual; 

3⁄4 cancellation of the limitations prescribed in PART IV^, thus returning 

to the retirement life (1000 hours) reported in Chapter 04 of the 

A109E Maintenance Manual; 

 

• a periodical check of the maximum allowable internal diameter of the 

bushing P/N 109-8131-30-109 (PART VI^). 

REQUIRED MANPOWER:

The following estimated manpower hours are required for compliance with this 

Bollettino: 

PART I^: Negligible. 

PART II^: Negligible. 

PART III^: 30 (thirty) minutes for each blade (magnifying glass 

inspection). 

PART IV^: 2 (two) hours for each pair of tail rotor blades 

P/N 109-8132-01-111. 

PART V^: 16 (sixteen) hours for the installation of the new bushings 

P/N 109-8131-30-109 inside the grips and a new pair of tail 

rotor blades P/N 109-8132-01-111;

 or 

6 (six) hours for the installation of the new grip and bushing 

assy P/N 109-8131-02-161 (refer to figure 2) and a new pair of 

tail rotor blades P/N 109-8132-01-111.

PART VI^: 7 (seven) hours to execute the inspection. 

WARRANTY:

The issue will be treated with a separate dedicated warranty policy letter. 

REQUIRED MATERIALS:

PART I^ and PART II^:

N.A. 
B.T. 109EP-30 

Page 5 of 18 

PART III^:

For the compliance with this PART of the Bollettino the following materials 

may be required: 

• Solvent (hexane or petroleum ether or aliphatic naphtha according to 

TT-N-95 type 2). 

• Visible dye penetrant P6R available from BRENT International; 

• nonaqueous wet developer 9D1B spray available from BRENT 

International; 

• one or more white light sources able to provide an illuminance of at least 

2000 lux on inspection area. 

CAUTION

It is prohibited to use alternative 

products of solvents, penetrant and 

developers to those specified in this 

Bollettino. 

PART IV^:

For the compliance of this PART of the Bollettino the following materials are 

required: 

P/N DENOMINATION Q.TY’

109-8132-01-111 Tail rotor blade A.R. 

LN94-20025 Cotter pin C.R. 

PART V^:

For the compliance of this PART of the Bollettino the following materials are 

required: 

P/N DENOMINATION Q.TY’

109-8131-30-109 Bushing 2 

RR187S Retainer ring 2 

 or 

M27426-3147D Retainer ring 2 

LN94-20025 Cotter pin 4 

109-8132-01-111 Tail rotor blade 2 

109-0131-27-101 Gasket assy 4 

each assy consists of: 

109-0131-27-103 Gasket .1 

109-0131-27-105 Ring .1 
B.T. 109EP-30 

Page 6 of 18 

Or alternatively at the operator’s discretion: 

P/N DENOMINATION Q.TY’

LN94-20025 Cotter pin 4 

109-8132-01-111 Tail rotor blade 2 

109-8131-02-161 Grip and bushing assy 2 

 (P/N assigned only for spare parts purposes) 

Each grip and bushing assy consists of (refer to figure 2): 

109-8131-29-101 Grip assy Ref. 

109-8131-30-109 Bushing Ref. 

109-8131-16-101 Washer Ref. 

RR187S Retainer ring Ref. 

 or 

M27426-3147D Retainer ring Ref. 

109-0131-27-101 Gasket assy Ref. 

In addition, the following consumable materials are required (normally 

commercially available but also available at Service Stations): 

SPECIFICATION DENOMINATION Q.TY’

MIL-P-23377 Primer A.R. 

 (cod. 900004523) 

MIL-T-81772 Thinner A.R. 

 (cod. 900002527) 

MIL-C-16173 Corrosion preventive compound A.R. 

Grade 2 (cod. 501221820) 

PART VI^:

The following materials may be necessary for compliance with this PART of 

the Bollettino: 

P/N DENOMINATION Q.TY’

109-8131-30-109 Bushing 1 

RR187S Retainer ring 1 

 or 

M27426-3147D Retainer ring 1 

109-0131-27-101 Gasket assy 2 

each gasket assy consists of: 

109-0131-27-103 Gasket .1 

109-0131-27-105 Ring .1 

SPECIAL TOOLS: 

• P/N 109-3130-56-111 (tool for the installation of the new bushings 

P/N 109-8131-30-109) ) consists of: 

3⁄4 n°1 Base P/N 109-3130-56-113 

3⁄4 n°1 Centering pin P/N 109-3130-56-115 

3⁄4 n°1 Pusher P/N 109-3130-56-119. 
B.T. 109EP-30 

Page 7 of 18 

• P/N 109-3130-72-101 (tool for the removal of the bushings 

P/N 109-0132-55). 

WEIGHT AND BALANCE CHANGES: 

PART I^, PART II^, PART III^ and PART IV^:

N.A. 

PART V^:

Negligible. 

PART VI^:

N.A. 

REFERENCES:

• A109E Maintenance Manual and applicable Temporary Revisions (refer to 

COMPLIANCE INSTRUCTIONS FOR PART V^ and PART VI^). 

• Pertinent A109E Rotorcraft Flight Manual and applicable Temporary 

Revisions (refer to COMPLIANCE INSTRUCTIONS FOR PART I^ and 

PART II^). 

PUBLICATIONS AFFECTED:

A109E Maintenance Manual. 

Pertinent A109E Rotorcraft Flight Manual. 

Pertinent A109E Illustrated Parts Catalog. 

A109E Overhaul Manual. 

COMPLIANCE INSTRUCTIONS:

PART I^:

1. Apply, on the central beam of the cockpit above the placard 

“Vne AIRSPEED LIMITATIONS – KIAS”, an adhesive label with the 

wording given below: 

Reduce all Vne by 28 KIAS 

optional equipment included

2. On the glass of the airspeed indicators apply a red mark over the value 

of 140 Kts. 
B.T. 109EP-30 

Page 8 of 18 

3. Insert in the Rotorcraft Flight Manual the pertinent Temporary 

Revisions. 

Helicopter Manual Temporary 

Revisions n° 

A109E equipped with 

Pratt&Whitney PW206C 

engines. 

Rotorcraft Flight Manual 

Agusta A109E 

(A109E RFM ) 

1-1 and 1-2. 

A109E equipped with 

Turbomeca Arrius 

TM2K1 engines. 

Rotorcraft Flight Manual 

Agusta A109E 

Turbomeca Arrius TM2K1 

Engine 

(A109E-RFM TM2K1) 

1-1 and 1-2. 

4. Record compliance with this PART of the Bollettino in the helicopter log 

book. 

PART II^:

NOTE

The procedure reported below must 

be performed on each one of the two 

tail rotor blades. 

CAUTION

If during the inspections cracks are 

found, remove from service the 

affected blade and consider it 

rejected. 

In this case inform: 

Agusta Service Engineering A109 

Tel. +39-0331711281 

Fax: +39-0331711397 

Fax: +39-0331711254 

1. Perform a visual check for cracks, on both upper and lower sides of 

blade in the area shown in figure 1. 

NOTE

Paint irregularities may be due to 

cracks. 
B.T. 109EP-30 

Page 9 of 18 

2. Insert in the Rotorcraft Flight Manual the pertinent Temporary 

Revisions. 

Helicopter Manual Temporary 

Revisions n° 

A109E equipped with 

Pratt&Whitney PW206C 

engines. 

Rotorcraft Flight Manual 

Agusta A109E 

(A109E RFM) 

2-3. 

A109E equipped with 

Turbomeca Arrius 

TM2K1 engines. 

Rotorcraft Flight Manual 

Agusta A109E 

Turbomeca Arrius TM2K1 

Engine 

(A109E-RFM TM2K1) 

2-5 and 2-6. 

3. Record compliance with this PART of the Bollettino in the helicopter log 

book. 

PART III^:

NOTE

The procedure reported below must 

be performed on each one of the two 

tail rotor blades. 

CAUTION

If during the inspections cracks are 

found, remove from service the 

affected blade and consider it 

rejected. 

In this case inform: 

Agusta Service Engineering A109 

Tel. +39-0331711281 

Fax: +39-0331711397 

Fax: +39-0331711254 

1. Prepare the helicopter on ground for a safe maintenance, disconnect 

any power source. 

2. Identify inspection area, on both upper and lower sides of the blade, in 

accordance with figure 1. 

3. Using a 5 power magnification lens, visually inspect area for cracks. 

Pay particular attention, on both upper and lower sides, to leading edge, 

along the blade in a chordwise sense corresponding to STA 540.00. 

4. Thoroughly degrease inspection area using a cloth soaked in solvent. 
B.T. 109EP-30 

Page 10 of 18 

5. Repeat inspection prescribed in above step 3. 

NOTE

Repeating this inspection with first 

the blade dirty and then the blade 

clean, is helpful in revealing the 

possible presence of cracks. 

CAUTION

If in doubt on the presence of cracks, 

accomplish the inspection with the 

liquid penetrant method as instructed 

below. 

6. Inspection with the liquid penetrant method: 

NOTE

This inspection must be performed 

without removing the paint, 

permitting the blades not to be 

removed from helicopter. 

6.1. It is possible to outline the area using only tape in which the adhesive 

does not absorb the solvent (ref. step 2). 

NOTE

During all inspection phases, the 

inspection area shall be lighted to 

2000 lux minimum. 

6.2. After the complete evaporation of the solvent (ref. step 4), perform the 

liquid penetrant inspection as follows: 

CAUTION

Personnel conducting the liquid 

penetrant inspection must be 

qualified in accordance with the 

ASNT practice SNT-TC-1A or other 

equivalent practice or standard. The 

blade, the penetrant and ambient 

temperatures shall be between 

15 and 45°C. 

6.2.1. Apply the penetrant P6R in the area identified in figure 1 for 

30 - 40 minutes dwell time. 
B.T. 109EP-30 

Page 11 of 18 

6.2.2. Remove excess penetrant firstly with a dry clean cloth and then a cloth 

dampened with solvent. 

Avoid soaking the cloth with solvent and most of all avoid direct contact 

of solvent with blade. 

6.2.3. After complete evaporation of solvent, apply the developer 9D1B 

spraying it from a distance of 30 - 40 cm. 

Prior to use, shake the spray can for at least 1 minute. 

CAUTION

To avoid any damage to the paint 

and/or problems in determining 

possible presence of cracks, the 

application of the developer must be 

accomplished in such a manner as to 

obtain a thin, even and uniform layer 

of developer. Under these 

circumstances when the developer is 

completely dry, the underlying paint 

color is clearly visible throughout. 

NOTE

A further application of developer, 

and consequently the entire 

inspection may not be repeated prior 

to an elapsed time of 24 hours. 

6.2.4. After 10 minutes of developer dwell time, carefully inspect the 

inspection area. 

Pay particular attention, on both upper and lower sides, to leading edge, 

along the blade in a chordwise sense corresponding to STA 540.00. 

6.2.5. After inspection, if no cracks are found, wait 15 minutes and clean 

affected area with a clean dry cloth and subsequently a cloth soaked in 

solvent to remove any developer residue. 

7. Return the helicopter in a ready to flight condition. 

8. Record compliance with this PART of the Bollettino in the helicopter log 

book. 

PART IV^:

1. Prepare the helicopter on ground for a safe maintenance, disconnect 

any power source. 

2. Remove and discard, tail rotor blades P/N 109-8132-01-111 affected by 

compliance of this PART of the Bollettino, in accordance with 

procedures reported in the A109E Maintenance Manual. 
B.T. 109EP-30 

Page 12 of 18 

CAUTION

The blades removed from service 

following compliance with PART IV^ 

of this Bollettino must be rejected 

and returned to Agusta. 

3. Install tail rotor blades P/N 109-8132-01-111 on the hub in accordance 

with the procedures reported in the A109E Maintenance Manual. 

NOTE

Use metric wrenches to apply torque 

as follows: 

• 

• 

wrench size #17 mm. for the bolt 

head; 

wrench size #19 mm. for the nut. 

4. Perform tail rotor dynamic balance in accordance with the procedures 

reported in the A109E Maintenance Manual. 

5. Return the helicopter in a ready to flight condition. 

6. Record compliance with this PART of the Bollettino in the helicopter log 

book. 

CAUTION

The blades that have been installed 

in compliance with this PART of the 

Bollettino shall be removed and 

discarded upon reaching 200 (two 

hundred) operating hours. 

PART V^:

NOTE

Compliance with this PART of the 

Bollettino permits: 

3⁄4 cancellation of the Vne limitations 

prescribed in PART I^, thus 

returning to the values reported in 

the pertinent A109E Rotorcraft 

Flight Manual; 

3⁄4 cancellation of the limitations 

prescribed in PART IV^, thus 

returning to the retirement life 

reported in Chapter 04 of the 

A109E Maintenance Manual. 
B.T. 109EP-30 

Page 13 of 18 

1. Prepare the helicopter on ground for safe maintenance, disconnect any 

power source. 

2. Remove tail rotor hub and blades assy in accordance with the 

procedures reported in the A109E Maintenance Manual. 

3. Remove and discard the tail rotor blades P/N 109-8132-01-111 in 

accordance with the procedures reported in the A109E Maintenance 

Manual. 

CAUTION

The blades removed from service 

following compliance with PART V^ 

of this Bollettino, must be rejected 

(irrespective of the accumulated 

operating hours) and returned to 

Agusta. 

4. Remove from hub, the grip assemblies P/N 109-8131-29-101, in 

accordance with the procedures reported in the A109E Maintenance 

Manual. 

5. Remove and discard the grip retainer ring P/N RR187S and gasket 

assemblies P/N 109-0131-27-101 from the grip. 

6. Heat the grips to a temperature of 80°C. Do not exceed this 

temperature. 

7. From each grip P/N 109-8131-29-101, remove and discard bushings 

P/N 109-0132-55 and spacer P/N 109-0132-13 in accordance with 

procedures reported in the A109E Maintenance Manual. 

NOTE

To remove bushings and spacer use 

tool P/N 109-3130-72-101 and a 

press. 

8. In addition, remove the washer P/N 109-8131-16-101 and put aside for 

later reuse. 

9. Accomplish installation of the new bushing P/N 109-8131-30-109 inside 

grip assy P/N 109-8131-29-101 as written below: 

NOTE

The procedure reported below must 

be performed on each one of the two 

tail rotor grips. 
B.T. 109EP-30 

Page 14 of 18 

9.1. Inspect and clean the grip in accordance with the procedures reported 

in the A109E Maintenance Manual. 

9.2. Install inside the grip the previously removed washer P/N 

109-8131-16-101 ensuring that chamfered side is inserted towards the 

bottom side of the grip. 

9.3. Install the gasket assemblies P/N 109-0131-27-101 inside the new 

bushing P/N 109-8131-30-109. 

9.4. Heat the grip to a temperature of 80°C. Do not exceed this temperature. 

9.5. Apply on bushing external surface a thin and uniform layer of thinned 

primer (MIL-P-23377 and MIL-T-81722). 

9.6. Install the new bushing P/N 109-8131-30-109 up to grip shoulder 

(complete with gasket assemblies P/N 109-0131-27-101), using the 

new tool P/N 109-3130-56-111 and a press. 

NOTE

Install the new bushing 

P/N 109-8131-30-109 while primer is 

still wet. 

9.7. Apply on the entire surface of the retainer ring P/N RR187S a thin and 

uniform layer of corrosion preventive compound spec. MIL-C-16173 

Grade 2, and install inside the grip. 

CAUTION

Using a red felt tip pen, apply a red 

mark on the outer surface of the 

external strap laminates, in proximity 

of the strap holes. 

During the installation of the grip and 

bushing assy, check that the red sign 

is visibile to ascertain that all the 

strap laminates have been correctly 

nested and none have accidentally 

been bent. 

10. Install on the tail rotor hub the grip and bushing assy in accordance with 

the procedures reported in the A109E Maintenance Manual. 

CAUTION

The promiscuous use of grips with 

bushings P/N 109-0132-55 and 

bushing P/N 109-8131-30-109 on the 

same hub is prohibited. 
B.T. 109EP-30 

Page 15 of 18 

NOTE

As an alternative to the operations 

given in steps 5. thru 9. it is possible 

to install a new grip and bushing 

assembly P/N 109-8131-02-161 for 

spare parts only (refer to figure 2). 

The grips and bushings removed 

from service following the installation 

of the new grips and bushings 

P/N 109-8131-02-161 shall be 

returned to Agusta. 

11. Install on the hub a pair of new tail rotor blades P/N 109-8132-01-111, 

in accordance with the procedures given in the A109E Maintenance 

Manual. 

CAUTION

It is prohibited to install tail rotor 

blades P/N 109-8132-01-111 that 

have accumulated more than 200 

(two hundred) operating hours on the 

hub and grips assemblies 

P/N 109-8131-02-127 (that installs 

the bushings P/N 109-0132-55). 

NOTE

Use metric wrenches to apply torque 

as follows: 

• 

• 

wrench size #17 mm. for the bolt 

head; 

wrench size #19 mm. for the nut. 

12. Using an etch pen, modify the P/N on the identification plate of the hub 

and grips assy with P/N 109-8131-02-159 in lieu of P/N 

109-8131-02-127. 

13. Using an etch pen, modify the P/N on the identification plate installed on 

the hub and blade assy with P/N 109-8131-02-157 in lieu of 

P/N 109-8131-02-151. 

14. Perform tail rotor dynamic balance in accordance with the A109E 

Maintenance Manual procedures. 

15. Remove the adhesive label, the red mark on the glass of the airspeed 

indicators and also remove and discard the associated Temporary 

Revisions prescribed in PART I^ of this Bollettino. 
B.T. 109EP-30 

Page 16 of 18 

16. Return the helicopter in a ready to flight condition. 

17. Insert in the A109E Maintenance Manual the following Temporary 

Revisions: 

Helicopter Manual Temporary 

Revisions n° 

A109E equipped with 

Pratt&Whitney PW206C 

engines and/or with 

Turbomeca Arrius TM2K1 

engines 

Maintenance Manual 

Agusta A109E 

(A109E-MM 

PW206C/TM2K1) 

00-1, 64-1, 64-2, 

and 64-4. 

18. Record compliance with this PART of the Bollettino in the helicopter log 

book. 

PART VI^:

1. Inspect lining of bushing P/N 109-8131-30-109 for wear and condition 

and measure internal diameter. Ensure that the value does not exceed 

41,35 mm. (refer to figure 2). 

CAUTION

If the resultant value is above 

41,35 mm, the bushing shall be 

removed from service and replaced 

with a new bushing of the same P/N. 

2. Insert in the A109E Maintenance Manual the following Temporary 

Revisions: 

Helicopter Manual Temporary 

Revisions n° 

A109E equipped with 

Pratt&Whitney PW206C 

engines and/or with 

Turbomeca Arrius TM2K1 

engines 

Maintenance Manual 

Agusta A109E 

(A109E-MM 

PW206C/TM2K1) 

05-6, 05-7 and 

64-3. 

3. Record compliance with this PART of the Bollettino in the helicopter log 

book. 
B.T. 109EP-30 

Page 17 of 18 
B.T. 109EP-30 

Page 18 of 18 

Drawing not in scale

FIGURE 2

(P/N 109-8131-02-161)